EP3604257B1 - Article comprising a fiber-reinforced self-healing bond coat - Google Patents
Article comprising a fiber-reinforced self-healing bond coat Download PDFInfo
- Publication number
- EP3604257B1 EP3604257B1 EP19189903.8A EP19189903A EP3604257B1 EP 3604257 B1 EP3604257 B1 EP 3604257B1 EP 19189903 A EP19189903 A EP 19189903A EP 3604257 B1 EP3604257 B1 EP 3604257B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- article
- fiber
- phase
- reinforcement structure
- substrate
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000000576 coating method Methods 0.000 claims description 38
- 239000011248 coating agent Substances 0.000 claims description 36
- 239000000835 fiber Substances 0.000 claims description 36
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 34
- 239000000758 substrate Substances 0.000 claims description 32
- 230000004888 barrier function Effects 0.000 claims description 26
- 239000000463 material Substances 0.000 claims description 26
- 230000007613 environmental effect Effects 0.000 claims description 24
- 239000011159 matrix material Substances 0.000 claims description 23
- 239000010703 silicon Substances 0.000 claims description 23
- 229910052710 silicon Inorganic materials 0.000 claims description 22
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 claims description 19
- 229910010271 silicon carbide Inorganic materials 0.000 claims description 19
- 239000000377 silicon dioxide Substances 0.000 claims description 17
- 239000000203 mixture Substances 0.000 claims description 16
- 229910052681 coesite Inorganic materials 0.000 claims description 14
- 229910052906 cristobalite Inorganic materials 0.000 claims description 14
- 229910052682 stishovite Inorganic materials 0.000 claims description 14
- 229910052905 tridymite Inorganic materials 0.000 claims description 14
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 10
- 239000011521 glass Substances 0.000 claims description 10
- 239000010410 layer Substances 0.000 claims description 10
- 229910052760 oxygen Inorganic materials 0.000 claims description 10
- 239000001301 oxygen Substances 0.000 claims description 10
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 9
- 239000011153 ceramic matrix composite Substances 0.000 claims description 8
- 229910052799 carbon Inorganic materials 0.000 claims description 6
- 229910052582 BN Inorganic materials 0.000 claims description 5
- PZNSFCLAULLKQX-UHFFFAOYSA-N Boron nitride Chemical compound N#B PZNSFCLAULLKQX-UHFFFAOYSA-N 0.000 claims description 5
- 239000007788 liquid Substances 0.000 claims description 5
- 239000011241 protective layer Substances 0.000 claims description 5
- 239000012530 fluid Substances 0.000 claims description 3
- 230000002787 reinforcement Effects 0.000 claims description 3
- 238000009834 vaporization Methods 0.000 claims description 2
- 230000008016 vaporization Effects 0.000 claims description 2
- 239000012071 phase Substances 0.000 description 27
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 22
- 230000015572 biosynthetic process Effects 0.000 description 10
- 239000007789 gas Substances 0.000 description 8
- 229910007217 Si(OH)x Inorganic materials 0.000 description 6
- 229910000676 Si alloy Inorganic materials 0.000 description 5
- 239000000919 ceramic Substances 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 229910010293 ceramic material Inorganic materials 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 3
- 239000002245 particle Substances 0.000 description 3
- BPQQTUXANYXVAA-UHFFFAOYSA-N Orthosilicate Chemical compound [O-][Si]([O-])([O-])[O-] BPQQTUXANYXVAA-UHFFFAOYSA-N 0.000 description 2
- 229910052581 Si3N4 Inorganic materials 0.000 description 2
- CSDREXVUYHZDNP-UHFFFAOYSA-N alumanylidynesilicon Chemical compound [Al].[Si] CSDREXVUYHZDNP-UHFFFAOYSA-N 0.000 description 2
- 238000013459 approach Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 229910002804 graphite Inorganic materials 0.000 description 2
- 239000010439 graphite Substances 0.000 description 2
- 239000007791 liquid phase Substances 0.000 description 2
- 229910001092 metal group alloy Inorganic materials 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 239000007800 oxidant agent Substances 0.000 description 2
- 229910052761 rare earth metal Inorganic materials 0.000 description 2
- 150000002910 rare earth metals Chemical class 0.000 description 2
- HQVNEWCFYHHQES-UHFFFAOYSA-N silicon nitride Chemical compound N12[Si]34N5[Si]62N3[Si]51N64 HQVNEWCFYHHQES-UHFFFAOYSA-N 0.000 description 2
- 238000005507 spraying Methods 0.000 description 2
- 239000000725 suspension Substances 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 1
- 229910003481 amorphous carbon Inorganic materials 0.000 description 1
- 238000000137 annealing Methods 0.000 description 1
- 229910052661 anorthite Inorganic materials 0.000 description 1
- 239000001569 carbon dioxide Substances 0.000 description 1
- 229910002092 carbon dioxide Inorganic materials 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 229910052593 corundum Inorganic materials 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 238000010285 flame spraying Methods 0.000 description 1
- 238000004108 freeze drying Methods 0.000 description 1
- 230000008014 freezing Effects 0.000 description 1
- 238000007710 freezing Methods 0.000 description 1
- 239000002241 glass-ceramic Substances 0.000 description 1
- CJNBYAVZURUTKZ-UHFFFAOYSA-N hafnium(IV) oxide Inorganic materials O=[Hf]=O CJNBYAVZURUTKZ-UHFFFAOYSA-N 0.000 description 1
- 229910000167 hafnon Inorganic materials 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- XWHPIFXRKKHEKR-UHFFFAOYSA-N iron silicon Chemical compound [Si].[Fe] XWHPIFXRKKHEKR-UHFFFAOYSA-N 0.000 description 1
- 238000011068 loading method Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 229910021471 metal-silicon alloy Inorganic materials 0.000 description 1
- 239000006060 molten glass Substances 0.000 description 1
- GALOTNBSUVEISR-UHFFFAOYSA-N molybdenum;silicon Chemical compound [Mo]#[Si] GALOTNBSUVEISR-UHFFFAOYSA-N 0.000 description 1
- LIZIAPBBPRPPLV-UHFFFAOYSA-N niobium silicon Chemical compound [Si].[Nb] LIZIAPBBPRPPLV-UHFFFAOYSA-N 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 230000001590 oxidative effect Effects 0.000 description 1
- 230000035699 permeability Effects 0.000 description 1
- 238000007750 plasma spraying Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 239000012779 reinforcing material Substances 0.000 description 1
- 235000012239 silicon dioxide Nutrition 0.000 description 1
- 238000002791 soaking Methods 0.000 description 1
- 239000007790 solid phase Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 239000012808 vapor phase Substances 0.000 description 1
- 230000004580 weight loss Effects 0.000 description 1
- 229910052882 wollastonite Inorganic materials 0.000 description 1
- 229910001845 yogo sapphire Inorganic materials 0.000 description 1
- 229910052845 zircon Inorganic materials 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/288—Protective coatings for blades
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
- C04B41/009—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone characterised by the material treated
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/622—Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/62222—Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products obtaining ceramic coatings
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/622—Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/626—Preparing or treating the powders individually or as batches ; preparing or treating macroscopic reinforcing agents for ceramic products, e.g. fibres; mechanical aspects section B
- C04B35/628—Coating the powders or the macroscopic reinforcing agents
- C04B35/62844—Coating fibres
- C04B35/62847—Coating fibres with oxide ceramics
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/622—Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/626—Preparing or treating the powders individually or as batches ; preparing or treating macroscopic reinforcing agents for ceramic products, e.g. fibres; mechanical aspects section B
- C04B35/628—Coating the powders or the macroscopic reinforcing agents
- C04B35/62844—Coating fibres
- C04B35/62857—Coating fibres with non-oxide ceramics
- C04B35/6286—Carbides
- C04B35/62863—Silicon carbide
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/622—Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/626—Preparing or treating the powders individually or as batches ; preparing or treating macroscopic reinforcing agents for ceramic products, e.g. fibres; mechanical aspects section B
- C04B35/628—Coating the powders or the macroscopic reinforcing agents
- C04B35/62844—Coating fibres
- C04B35/62857—Coating fibres with non-oxide ceramics
- C04B35/62865—Nitrides
- C04B35/62868—Boron nitride
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/622—Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/626—Preparing or treating the powders individually or as batches ; preparing or treating macroscopic reinforcing agents for ceramic products, e.g. fibres; mechanical aspects section B
- C04B35/628—Coating the powders or the macroscopic reinforcing agents
- C04B35/62844—Coating fibres
- C04B35/62857—Coating fibres with non-oxide ceramics
- C04B35/62873—Carbon
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
- C04B41/45—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements
- C04B41/4505—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements characterised by the method of application
- C04B41/4523—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements characterised by the method of application applied from the molten state ; Thermal spraying, e.g. plasma spraying
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
- C04B41/45—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements
- C04B41/52—Multiple coating or impregnating multiple coating or impregnating with the same composition or with compositions only differing in the concentration of the constituents, is classified as single coating or impregnation
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
- C04B41/80—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone of only ceramics
- C04B41/81—Coating or impregnation
- C04B41/89—Coating or impregnation for obtaining at least two superposed coatings having different compositions
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2111/00—Mortars, concrete or artificial stone or mixtures to prepare them, characterised by specific function, property or use
- C04B2111/00474—Uses not provided for elsewhere in C04B2111/00
- C04B2111/00982—Uses not provided for elsewhere in C04B2111/00 as construction elements for space vehicles or aeroplanes
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/30—Constituents and secondary phases not being of a fibrous nature
- C04B2235/34—Non-metal oxides, non-metal mixed oxides, or salts thereof that form the non-metal oxides upon heating, e.g. carbonates, nitrates, (oxy)hydroxides, chlorides
- C04B2235/3418—Silicon oxide, silicic acids, or oxide forming salts thereof, e.g. silica sol, fused silica, silica fume, cristobalite, quartz or flint
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/30—Constituents and secondary phases not being of a fibrous nature
- C04B2235/38—Non-oxide ceramic constituents or additives
- C04B2235/3817—Carbides
- C04B2235/3826—Silicon carbides
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/30—Constituents and secondary phases not being of a fibrous nature
- C04B2235/38—Non-oxide ceramic constituents or additives
- C04B2235/3852—Nitrides, e.g. oxynitrides, carbonitrides, oxycarbonitrides, lithium nitride, magnesium nitride
- C04B2235/386—Boron nitrides
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/30—Constituents and secondary phases not being of a fibrous nature
- C04B2235/42—Non metallic elements added as constituents or additives, e.g. sulfur, phosphor, selenium or tellurium
- C04B2235/422—Carbon
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
- C04B2235/52—Constituents or additives characterised by their shapes
- C04B2235/5208—Fibers
- C04B2235/5216—Inorganic
- C04B2235/524—Non-oxidic, e.g. borides, carbides, silicides or nitrides
- C04B2235/5244—Silicon carbide
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/70—Aspects relating to sintered or melt-casted ceramic products
- C04B2235/96—Properties of ceramic products, e.g. mechanical properties such as strength, toughness, wear resistance
- C04B2235/9669—Resistance against chemicals, e.g. against molten glass or molten salts
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/15—Rare earth metals, i.e. Sc, Y, lanthanides
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/20—Oxide or non-oxide ceramics
- F05D2300/22—Non-oxide ceramics
- F05D2300/222—Silicon
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/20—Oxide or non-oxide ceramics
- F05D2300/22—Non-oxide ceramics
- F05D2300/226—Carbides
- F05D2300/2261—Carbides of silicon
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/20—Oxide or non-oxide ceramics
- F05D2300/22—Non-oxide ceramics
- F05D2300/228—Nitrides
- F05D2300/2283—Nitrides of silicon
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/603—Composites; e.g. fibre-reinforced
- F05D2300/6033—Ceramic matrix composites [CMC]
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/611—Coating
Definitions
- the disclosure relates to an article comprising a substrate containing silicon and an environmental barrier coating (EBC) which functions as a protective environmental barrier coating and inhibits the formation of gaseous species of Si, particularly Si(OH) x when the article is exposed to a high temperature, steam-laden environment.
- EBC environmental barrier coating
- Ceramic materials containing silicon and metal alloys containing silicon have been proposed for structures used in high temperature applications as, for example, gas turbine engines, heat exchangers, internal combustion engines, and the like.
- a particularly useful application for these materials is for service in gas turbine engines which operate at high temperatures in steam-laden environments.
- the ceramic materials that operate within the gas turbine are exposed to an environment in which jet fuel is combusted. As a result of the combustion, the temperature is high and steam (vapor phase water) and oxygen are present.
- silicon containing substrates can recede and lose mass as a result of a formation of volatile Si species, particularly Si(OH) x and SiO when exposed to high temperature, steam laden environments.
- volatile Si species particularly Si(OH) x and SiO
- silicon carbide when exposed to a lean fuel environment of approximately 1 ATM pressure of water vapor at 1200°C will exhibit weight loss and recession at a rate of approximately 6 mils per 1000 hrs.
- the substrate comprises a ceramic matrix composite (CMC) material.
- CMC ceramic matrix composite
- the fiber-reinforcement structure comprises a SiC material composition.
- the substrate comprises a turbine blade, and the load bearing stress direction is oriented along a root to tip direction.
- the substrate comprises at least one of a turbine vane and a turbine blade, and the load bearing stress direction is oriented along the contour of a platform fillet.
- the fiber-reinforcement structure comprises fibers that are oxygen getter loading materials.
- the fiber-reinforcement structure comprises fibers that are coated with an interface coating.
- the interface coating is selected from the group consisting of boron nitride, silicon carbide, an oxide and carbon.
- the matrix comprises a multi-phase mixture.
- the multi-phase mixture comprises SiO 2 .
- the self-healing phase comprises a glass phase.
- the self-healing phase comprises a material having properties of being in thermodynamic equilibrium with SiO 2 during operation at predetermined temperatures.
- the self-healing phase comprises a material having properties of flowing into cracks formed in the matrix during operation at predetermined temperatures of between 1000°C and 2000°C.
- the environmental barrier coating further comprises an oxygen getter phase interspersed throughout the matrix.
- the environmental barrier coating further comprises a protective layer applied on the environmental barrier coating.
- the disclosure relates to a continuous fiber-reinforced, self-healing environmental barrier coating that prevents the ingress of oxygen and steam.
- the disclosed coating can increase durability with respect to conventional coatings.
- This coating consists of an oxide matrix and continuous fibers in a woven structure.
- the oxide matrix is a multi-phase mixture consisting of at least a SiO 2 rich phase and a glass phase.
- the oxide matrix can be a single phase material that may not include a self-healing functionality.
- the composition of the glass phase is chosen to be in thermodynamic equilibrium with SiO 2 and to be sufficiently fluid at high temperatures to flow into cracks in the coating, which imparts 'self-healing functionality.
- the fibers could be SiC, in some instances coated with an interface coating, such as boron nitride or silicon carbide, oxide (e.g. Nextel TM 720) or carbon.
- an environmental barrier coating 10 formed over a substrate 12 of an article 14, configured to inhibit the formation of gaseous species of silicon when the article 14 is exposed to a high temperature, steam-laden environment.
- the coating 10 can be designed for maximum protection between 1100°C and 1700°C.
- the substrate 12 can be associated with articles 14 such as, at least one of a turbine vane and a turbine blade, and particularly a gas turbine engine component, such as components in the hot section of the gas turbine engine, including rotating components and portions of combustors, shrouds, and the like.
- the substrate 12 of the article 14 can include portions that experience certain forces that result in a load bearing stress often oriented in a particular direction, i.e., a load bearing stress direction 16 of the substrate 12 of the article 14, illustrated as an arrow 16. It is contemplated that the load bearing stress direction 16 can be oriented in a variety of directions as well as multiple directions depending on the design of the substrate 12 and service of the article 14 in the gas turbine engine.
- the load bearing stress direction 16 can be oriented from a root 18 of the article 14 to a tip 20 of the article 14, such as a blade root to a blade tip.
- the load bearing stress direction 16 can be oriented along a contour of a fillet between a platform and an airfoil portion of the article 14, such as a blade/vane platform fillet 22.
- the root to tip direction can be understood as orthogonal to the plane of the page shown in the bundle of fibers 38.
- the substrate 12 can be constructed from materials containing silicon and can be a ceramic matrix composite material, a silicon ceramic substrate or a silicon containing metal alloy.
- the substrate 12 can be silicon containing ceramic material such as, for example, silicon carbide, silicon nitride, silicon oxy-nitride and silicon aluminum oxy-nitride.
- the silicon containing ceramic substrate comprises a silicon containing matrix with reinforcing materials 24 such as fibers, particles and the like and, more particularly, a silicon based matrix which is fiber-reinforced.
- Particularly suitable ceramic substrates are a silicon carbide coated silicon carbide fiber-reinforced silicon carbide particle and silicon matrix, a carbon fiber-reinforced silicon carbide matrix and a silicon carbide fiber-reinforced silicon nitride matrix.
- Particularly useful silicon-metal alloys for use as substrates for the article 14 can include molybdenum-silicon alloys, niobium-silicon alloys, iron-silicon alloys, and aluminum-silicon alloys.
- an environmental barrier layer 26 can be applied to the substrate 14.
- a protective layer 28 can be applied on the environmental barrier layer 26.
- the protective layer 28 is configured to resist vaporization when exposed to steam.
- the protective layer can be a rare earth disilicate, such as Y 2 Si 2 O 7 , Yb 2 Si 2 O 7 ; a rare earth monosilicate, such as Y 2 SiO 5 , Yb 2 SiO 5 , HfSiO 4 , ZrSiO 4 , HfO 2 , BSAS (Ba x Sr 1-x Al 2 Si 2 O 8 where x may be 0.25) .
- the environmental barrier layer 26 includes an oxide matrix 30 surrounding a fiber-reinforcement structure 32 and a self-healing phase 34 interspersed throughout the oxide matrix 30.
- the oxide matrix 30 can be a single phase without self-healing phase present.
- the oxide matrix 30 can include a multi-phase mixture, such as SiO 2 rich phase.
- the self-healing phase 34 can include a glass phase.
- the self-healing phase 34 can include a material having properties that are in thermodynamic equilibrium with SiO 2 during operation at predetermined temperatures.
- the self-healing phase 34 comprises a material having properties of flowing into cracks 48 formed in the matrix 30 during operation at those predetermined temperatures.
- the self-healing phase 34 can be sufficiently fluid at high temperatures to flow into cracks 48 in the coating 10, which imparts a self-healing functionality. Between 1000°C and 2000°C these materials can exist as mixtures of solid and liquid phases.
- the temperature at which liquid formation occurs can be controlled by the chemical composition. In an exemplary embodiment, liquid formation initiates between 1150°C and 1500°C, with the volume fraction of liquid increasing with temperature.
- the viscosity of the liquid phase can vary from 0.1 to 100,000 Pa*s with the exemplary viscosity varying between 10-10,000 Pa*s.
- An example of the self-healing phase 34 can include a mixture of BaMg 2 Al 6 Si 9 O 30 and SiO 2 .
- Another example can include the mixture of CaAl 2 Si 2 O 8 , CaSiO 3 and SiO 2 .
- Another example includes the mixture of Y 2 Si 2 O 7 , Al 2 O 3 and SiO 2 .
- the materials listed above could be premixed and processed to form a glass.
- the initial composition of the glass could be: 2%BaO,3%MgO, 10%AlO 1.5 , 85% SiO 2 , or 8% CaO, 17%AlO 1.5 75% SiO 2 , or 10% YO 1.5 , 10 AlO 1.5 , 80%SiO 2 .
- An oxygen getter phase 36 can also be interspersed throughout the oxide matrix 30.
- the oxygen getter phase 36 can comprise an oxy-carbide material.
- the oxy-carbide material can include a glass that contains oxygen and carbon and silicon dioxide as well as particles of amorphous carbon and silicon carbide.
- the fiber-reinforcement structure 32 includes a continuous weave of fibers.
- the fiber-reinforcement structure 32 comprises a SiC material composition.
- the fiber-reinforcement structure 32 includes at least one first fiber bundle 38 oriented along the load bearing stress direction 16 of the substrate 12.
- the first fiber bundle 38 can be oriented from blade root 18 to blade tip 20 and aligned along the root to tip direction, so as to provide structural support along the same orientation as the load bearing stress direction 16.
- the first fiber bundle 38 can be oriented along the load bearing stress direction 16 oriented along the contour of the blade/vane platform fillet 22.
- the fiber-reinforcement structure 32 comprises at least one second fiber bundle 40 oriented orthogonal to the first fiber bundle 38 orientation.
- the fiber-reinforcement structure 32 also comprises at least one third fiber 42 woven between the first fiber bundle 38 and the second fiber bundle 40.
- the fiber-reinforcement structure 32 comprises fibers that comprise oxygen getter materials 44.
- the fiber-reinforcement structure 32 comprises fibers that are coated with an interface coating 46.
- the interface coating 46 can include materials selected from the group consisting of boron nitride, silicon carbide, an oxide and carbon.
- the environmental barrier layer 26 can be present on the article at a thickness of greater than or equal to about 0.5 mils (0.0005 inch), preferably between about 3 to about 30 mils and ideally between about 3 to about 8 mils.
- the environmental barrier layer 26 can be applied by preparing the substrate 14 surface.
- a fiber preform can be infiltrated using a glass particulate suspension, which would be added to the fiber preform layer by soaking, spraying or other means, at ambient temperature.
- the infiltrated fabric or preform is placed adjacent to the silicon containing CMC substrate 12, and the assembly is heated.
- Pressure can be applied using graphite dies, powdered media such as carbon or boron nitride, and the like, in order to de-gas the environmental barrier layer 26 at temperatures suitable for melting the glass.
- the subsequent assembly can undergo annealing to obtain a desired microstructure.
- an alternate technique of assembly would be to place a fiber preform in contact with the silicon containing CMC substrate 12.
- the fiber perform can then be rigidized using a variety of techniques, including but not limited to adding a ceramic sol and freezing the substrate followed by freeze drying.
- the assembly is then placed into a graphite die which comprises an outer profile of the EBC coated article 14. Molten glass is then injected into the die and flows into and among the fibers of the preform.
- the assembly can then be cooled and (re)heated to a temperature suitable to promote the formation of the desired microstructure.
- Alternative approaches to introducing oxide or silicate phases into a relatively thin fiber preform can include but are not limited to spraying the preform with a suspension, followed by heating the surface via flame or plasma spraying molten oxide and/or silicate materials onto the preform, and the like. Generally, avoiding sharp temperature gradients between the substrate and the created layer should be avoided to enhance adherence.
- a self-healing, fiber-reinforced oxidant barrier offers a robust mechanism for protecting load bearing materials in the hot-section of gas turbine engines.
- This disclosure describes the use of fiber reinforcements in the environmental barrier coating to increase durability. Additionally, the self-healing, multi-phase matrix that surrounds the fibers inhibits the permeability of oxidants through the coating. The fibers will also increase the creep resistance of the coating, enhancing durability on rotating components.
- An environmental barrier coating prevents CMC recession caused by Si(OH)x formation. Interaction of the environmental barrier coating with the steam laden combustion environment results in the formation of Si(OH)x, but the rate of formation is much less than that of an uncoated SiC CMC.
Description
- The disclosure relates to an article comprising a substrate containing silicon and an environmental barrier coating (EBC) which functions as a protective environmental barrier coating and inhibits the formation of gaseous species of Si, particularly Si(OH)x when the article is exposed to a high temperature, steam-laden environment.
- Ceramic materials containing silicon and metal alloys containing silicon have been proposed for structures used in high temperature applications as, for example, gas turbine engines, heat exchangers, internal combustion engines, and the like. A particularly useful application for these materials is for service in gas turbine engines which operate at high temperatures in steam-laden environments. The ceramic materials that operate within the gas turbine are exposed to an environment in which jet fuel is combusted. As a result of the combustion, the temperature is high and steam (vapor phase water) and oxygen are present.
- It has been found that these silicon containing substrates can recede and lose mass as a result of a formation of volatile Si species, particularly Si(OH)x and SiO when exposed to high temperature, steam laden environments. For example, silicon carbide when exposed to a lean fuel environment of approximately 1 ATM pressure of water vapor at 1200°C will exhibit weight loss and recession at a rate of approximately 6 mils per 1000 hrs.
- It is believed that the process involves oxidation of the silicon carbide to form silica on the surface of the silicon carbide followed by reaction of the silica with steam to form volatile species of silicon such as Si(OH)x. Naturally it would be highly desirable to provide an external barrier coating for silicon containing substrates which would inhibit the formation of volatile silicon species, Si(OH)x and SiO, and thereby reduce recession and mass loss.
WO2014204480A1 ,EP2615250A1 ,EP189504A1 EP2644747A2 disclose environmental barrier coatings of the prior art. - In an aspect of the invention an article is provided in accordance with claim 1.
- In another and alternative embodiment, the substrate comprises a ceramic matrix composite (CMC) material.
- In another and alternative embodiment, the fiber-reinforcement structure comprises a SiC material composition.
- In another and alternative embodiment, the substrate comprises a turbine blade, and the load bearing stress direction is oriented along a root to tip direction.
- In another and alternative embodiment, the substrate comprises at least one of a turbine vane and a turbine blade, and the load bearing stress direction is oriented along the contour of a platform fillet.
- In another and alternative embodiment, the fiber-reinforcement structure comprises fibers that are oxygen getter loading materials.
- In another and alternative embodiment, the fiber-reinforcement structure comprises fibers that are coated with an interface coating.
- In another and alternative embodiment, the interface coating is selected from the group consisting of boron nitride, silicon carbide, an oxide and carbon.
- In another and alternative embodiment, the matrix comprises a multi-phase mixture.
- In another and alternative embodiment, the multi-phase mixture comprises SiO2.
- In another and alternative embodiment, the self-healing phase comprises a glass phase.
- In another and alternative embodiment, the self-healing phase comprises a material having properties of being in thermodynamic equilibrium with SiO2 during operation at predetermined temperatures.
- In another and alternative embodiment, the self-healing phase comprises a material having properties of flowing into cracks formed in the matrix during operation at predetermined temperatures of between 1000°C and 2000°C.
- In another and alternative embodiment, the environmental barrier coating further comprises an oxygen getter phase interspersed throughout the matrix.
- In another and alternative embodiment, the environmental barrier coating further comprises a protective layer applied on the environmental barrier coating.
- The disclosure relates to a continuous fiber-reinforced, self-healing environmental barrier coating that prevents the ingress of oxygen and steam. The disclosed coating can increase durability with respect to conventional coatings. This coating consists of an oxide matrix and continuous fibers in a woven structure. The oxide matrix is a multi-phase mixture consisting of at least a SiO2 rich phase and a glass phase. In alternative embodiments, the oxide matrix can be a single phase material that may not include a self-healing functionality. The composition of the glass phase is chosen to be in thermodynamic equilibrium with SiO2 and to be sufficiently fluid at high temperatures to flow into cracks in the coating, which imparts 'self-healing functionality.' The fibers could be SiC, in some instances coated with an interface coating, such as boron nitride or silicon carbide, oxide (e.g. Nextel™ 720) or carbon.
- Other details of the coating are set forth in the following detailed description and the accompanying drawings wherein like reference numerals depict like elements.
-
-
FIG. 1 is a cross section of an exemplary coating on a substrate containing silicon according to the disclosure. -
FIG. 2 is a cross section of an exemplary coating on a substrate containing silicon according to the disclosure. -
FIG. 3 is cross section of the exemplary coating on a substrate containing silicon according to the disclosure. - Referring now to
FIG. 1 , there is illustrated anenvironmental barrier coating 10 formed over asubstrate 12 of anarticle 14, configured to inhibit the formation of gaseous species of silicon when thearticle 14 is exposed to a high temperature, steam-laden environment. Thecoating 10 can be designed for maximum protection between 1100°C and 1700°C. Thesubstrate 12 can be associated witharticles 14 such as, at least one of a turbine vane and a turbine blade, and particularly a gas turbine engine component, such as components in the hot section of the gas turbine engine, including rotating components and portions of combustors, shrouds, and the like. - The
substrate 12 of thearticle 14 can include portions that experience certain forces that result in a load bearing stress often oriented in a particular direction, i.e., a load bearingstress direction 16 of thesubstrate 12 of thearticle 14, illustrated as anarrow 16. It is contemplated that the load bearingstress direction 16 can be oriented in a variety of directions as well as multiple directions depending on the design of thesubstrate 12 and service of thearticle 14 in the gas turbine engine. - In an exemplary embodiment the load bearing
stress direction 16 can be oriented from aroot 18 of thearticle 14 to a tip 20 of thearticle 14, such as a blade root to a blade tip. In another exemplary embodiment, the load bearingstress direction 16 can be oriented along a contour of a fillet between a platform and an airfoil portion of thearticle 14, such as a blade/vane platform fillet 22. As illustrated inFIG 3 , the root to tip direction can be understood as orthogonal to the plane of the page shown in the bundle offibers 38. - The
substrate 12 can be constructed from materials containing silicon and can be a ceramic matrix composite material, a silicon ceramic substrate or a silicon containing metal alloy. In an exemplary embodiment, thesubstrate 12 can be silicon containing ceramic material such as, for example, silicon carbide, silicon nitride, silicon oxy-nitride and silicon aluminum oxy-nitride. In accordance with a particular embodiment, the silicon containing ceramic substrate comprises a silicon containing matrix with reinforcingmaterials 24 such as fibers, particles and the like and, more particularly, a silicon based matrix which is fiber-reinforced. Particularly suitable ceramic substrates are a silicon carbide coated silicon carbide fiber-reinforced silicon carbide particle and silicon matrix, a carbon fiber-reinforced silicon carbide matrix and a silicon carbide fiber-reinforced silicon nitride matrix. Particularly useful silicon-metal alloys for use as substrates for thearticle 14 can include molybdenum-silicon alloys, niobium-silicon alloys, iron-silicon alloys, and aluminum-silicon alloys. - Referring also to
FIG. 2 andFIG. 3 , anenvironmental barrier layer 26 can be applied to thesubstrate 14. Aprotective layer 28 can be applied on theenvironmental barrier layer 26. Theprotective layer 28 is configured to resist vaporization when exposed to steam. In an exemplary embodiment, the protective layer can be a rare earth disilicate, such as Y2Si2O7, Yb2Si2O7; a rare earth monosilicate, such as Y2SiO5, Yb2SiO5, HfSiO4, ZrSiO4, HfO2, BSAS (BaxSr1-xAl2Si2O8 where x may be 0.25) . - The
environmental barrier layer 26 includes anoxide matrix 30 surrounding a fiber-reinforcement structure 32 and a self-healing phase 34 interspersed throughout theoxide matrix 30. In an alternative embodiment, not according to the invention, theoxide matrix 30 can be a single phase without self-healing phase present. In another embodiment, theoxide matrix 30 can include a multi-phase mixture, such as SiO2 rich phase. The self-healing phase 34 can include a glass phase. The self-healing phase 34 can include a material having properties that are in thermodynamic equilibrium with SiO2 during operation at predetermined temperatures. The self-healing phase 34 comprises a material having properties of flowing intocracks 48 formed in thematrix 30 during operation at those predetermined temperatures. The self-healing phase 34 can be sufficiently fluid at high temperatures to flow intocracks 48 in thecoating 10, which imparts a self-healing functionality. Between 1000°C and 2000°C these materials can exist as mixtures of solid and liquid phases. The temperature at which liquid formation occurs can be controlled by the chemical composition. In an exemplary embodiment, liquid formation initiates between 1150°C and 1500°C, with the volume fraction of liquid increasing with temperature. The viscosity of the liquid phase can vary from 0.1 to 100,000 Pa*s with the exemplary viscosity varying between 10-10,000 Pa*s. An example of the self-healing phase 34 can include a mixture of BaMg2Al6Si9O30 and SiO2. Another example can include the mixture of CaAl2Si2O8, CaSiO3 and SiO2. Another example includes the mixture of Y2Si2O7, Al2O3 and SiO2. Alternatively, the materials listed above could be premixed and processed to form a glass. The initial composition of the glass could be: 2%BaO,3%MgO, 10%AlO1.5, 85% SiO2, or 8% CaO, 17%AlO1.5 75% SiO2, or 10% YO1.5, 10 AlO1.5, 80%SiO2. - An
oxygen getter phase 36 can also be interspersed throughout theoxide matrix 30. Theoxygen getter phase 36 can comprise an oxy-carbide material. In an exemplary embodiment, the oxy-carbide material can include a glass that contains oxygen and carbon and silicon dioxide as well as particles of amorphous carbon and silicon carbide. - The fiber-
reinforcement structure 32 includes a continuous weave of fibers. In an exemplary embodiment, the fiber-reinforcement structure 32 comprises a SiC material composition. The fiber-reinforcement structure 32 includes at least onefirst fiber bundle 38 oriented along the load bearingstress direction 16 of thesubstrate 12. In an exemplary embodiment, thefirst fiber bundle 38 can be oriented fromblade root 18 to blade tip 20 and aligned along the root to tip direction, so as to provide structural support along the same orientation as the load bearingstress direction 16. In another exemplary embodiment, thefirst fiber bundle 38 can be oriented along the load bearingstress direction 16 oriented along the contour of the blade/vane platform fillet 22. - In accordance with the invention, the fiber-
reinforcement structure 32 comprises at least onesecond fiber bundle 40 oriented orthogonal to thefirst fiber bundle 38 orientation. The fiber-reinforcement structure 32 also comprises at least onethird fiber 42 woven between thefirst fiber bundle 38 and thesecond fiber bundle 40. In an exemplary embodiment, the fiber-reinforcement structure 32 comprises fibers that compriseoxygen getter materials 44. In another exemplary embodiment, the fiber-reinforcement structure 32 comprises fibers that are coated with aninterface coating 46. Theinterface coating 46 can include materials selected from the group consisting of boron nitride, silicon carbide, an oxide and carbon. - The
environmental barrier layer 26 can be present on the article at a thickness of greater than or equal to about 0.5 mils (0.0005 inch), preferably between about 3 to about 30 mils and ideally between about 3 to about 8 mils. - The
environmental barrier layer 26 can be applied by preparing thesubstrate 14 surface. - There are several methods that could be used to introduce a glass-ceramic into the
fiber reinforcement structure 32 being provided for theenvironmental barrier coating 10. In one approach, a fiber preform can be infiltrated using a glass particulate suspension, which would be added to the fiber preform layer by soaking, spraying or other means, at ambient temperature. The infiltrated fabric or preform is placed adjacent to the silicon containingCMC substrate 12, and the assembly is heated. Pressure can be applied using graphite dies, powdered media such as carbon or boron nitride, and the like, in order to de-gas theenvironmental barrier layer 26 at temperatures suitable for melting the glass. The subsequent assembly can undergo annealing to obtain a desired microstructure. - In another exemplary embodiment, an alternate technique of assembly would be to place a fiber preform in contact with the silicon containing
CMC substrate 12. The fiber perform can then be rigidized using a variety of techniques, including but not limited to adding a ceramic sol and freezing the substrate followed by freeze drying. The assembly is then placed into a graphite die which comprises an outer profile of the EBC coatedarticle 14. Molten glass is then injected into the die and flows into and among the fibers of the preform. The assembly can then be cooled and (re)heated to a temperature suitable to promote the formation of the desired microstructure. - Alternative approaches to introducing oxide or silicate phases into a relatively thin fiber preform, can include but are not limited to spraying the preform with a suspension, followed by heating the surface via flame or plasma spraying molten oxide and/or silicate materials onto the preform, and the like. Generally, avoiding sharp temperature gradients between the substrate and the created layer should be avoided to enhance adherence.
- A self-healing, fiber-reinforced oxidant barrier offers a robust mechanism for protecting load bearing materials in the hot-section of gas turbine engines. This disclosure describes the use of fiber reinforcements in the environmental barrier coating to increase durability. Additionally, the self-healing, multi-phase matrix that surrounds the fibers inhibits the permeability of oxidants through the coating. The fibers will also increase the creep resistance of the coating, enhancing durability on rotating components.
- An environmental barrier coating prevents CMC recession caused by Si(OH)x formation. Interaction of the environmental barrier coating with the steam laden combustion environment results in the formation of Si(OH)x, but the rate of formation is much less than that of an uncoated SiC CMC.
- There has been provided a coating. While the coating has been described in the context of specific embodiments thereof, other unforeseen alternatives, modifications, and variations may become apparent to those skilled in the art having read the foregoing description. Accordingly, it is intended to embrace those alternatives, modifications, and variations which fall within the broad scope of the appended claims.
Claims (15)
- An article comprising:a substrate (12) containing silicon; andan environmental barrier coating (10), the environmental barrier coating (10) comprising:
an environmental barrier layer (26) applied to the substrate (12); said environmental barrier layer (26) comprising an oxide matrix (30) surrounding a fiber-reinforcement structure (32) and a self-healing phase (34) interspersed throughout said oxide matrix (30), wherein said self-healing phase (34) comprises a material configured to form a liquid and be sufficiently fluid to flow into cracks (48) formed in said oxide matrix (30) during operation at predetermined temperatures;wherein said fiber-reinforcement structure (32) comprises a continuous weave of fibers;wherein the substrate (12) includes portions that are configured to experience forces in a load bearing stress direction (16);wherein said fiber-reinforcement structure (32) comprises at least one first fiber bundle (38) oriented along the load bearing stress direction (16) of said substrate (12);wherein said fiber-reinforcement structure (32) comprises at least one second fiber bundle (40) oriented orthogonal to said first fiber bundle (38) orientation;wherein said fiber reinforcement structure (32) comprises at least one third fiber (42) woven between said first fiber bundle (38) and said second fiber bundle (40). - The article of claim 1, wherein said substrate (12) comprises a ceramic matrix composite material.
- The article of claim 1 or 2, wherein said fiber-reinforcement structure (32) comprises a SiC material composition.
- The article of any preceding claim, wherein the article (14) comprises a turbine blade, and said load bearing stress direction (16) is oriented along a root (18) to tip (20) direction of the turbine blade.
- The article of any of claims 1-3, wherein said article (14) comprises at least one of a turbine vane and a turbine blade, and said load bearing stress direction (16) is oriented along a contour of a fillet (22) between a platform and an airfoil portion of the article (14).
- The article of any preceding claim, wherein the environmental barrier coating further comprises an oxygen getter phase (36) interspersed throughout said matrix, wherein the oxygen getter phase (36) comprises an oxy-carbide material.
- The article of any preceding claim, wherein said fiber-reinforcement structure (32) comprises fibers that are coated with an interface coating (46).
- The article of claim 7, wherein said interface coating (46) is selected from the group consisting of boron nitride, silicon carbide, an oxide and carbon.
- The article of any preceding claim, wherein said oxide matrix (30) comprises a multi-phase mixture.
- The article of claim 9, wherein said multi-phase mixture comprises SiO2.
- The article of any preceding claim, wherein said self-healing phase (34) comprises a glass phase.
- The article of any preceding claim, the material is configured to be in thermodynamic equilibrium with SiO2 during operation at the predetermined temperatures.
- The article of any preceding claim, wherein the predetermined temperatures are between 1000°C and 2000°C.
- The article of any preceding claim, wherein the material is configured to initiate forming the liquid at a temperature between 1150°C and 1500°C.
- The article of any preceding claim, further comprising:
a protective layer (28) configured to resist vaporization when exposed to steam applied on said environmental barrier coating (10).
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US16/054,015 US11668198B2 (en) | 2018-08-03 | 2018-08-03 | Fiber-reinforced self-healing environmental barrier coating |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3604257A1 EP3604257A1 (en) | 2020-02-05 |
EP3604257B1 true EP3604257B1 (en) | 2022-04-06 |
Family
ID=67658414
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP19189903.8A Active EP3604257B1 (en) | 2018-08-03 | 2019-08-02 | Article comprising a fiber-reinforced self-healing bond coat |
Country Status (2)
Country | Link |
---|---|
US (1) | US11668198B2 (en) |
EP (1) | EP3604257B1 (en) |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US11668198B2 (en) | 2018-08-03 | 2023-06-06 | Raytheon Technologies Corporation | Fiber-reinforced self-healing environmental barrier coating |
US11505506B2 (en) * | 2018-08-16 | 2022-11-22 | Raytheon Technologies Corporation | Self-healing environmental barrier coating |
US11535571B2 (en) | 2018-08-16 | 2022-12-27 | Raytheon Technologies Corporation | Environmental barrier coating for enhanced resistance to attack by molten silicate deposits |
US10927705B2 (en) * | 2018-08-17 | 2021-02-23 | Raytheon Technologies Corporation | Method for forming cooling holes having separate complex and simple geometry sections |
US11697623B2 (en) * | 2020-06-18 | 2023-07-11 | Rolls-Royce Corporation | Method to produce a ceramic matrix composite with controlled surface characteristics |
Family Cites Families (97)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1170592A (en) * | 1966-11-29 | 1969-11-12 | Rolls Royce | Aerofoil-Shaped Blades and Blade Assemblies, for use in a Fluid Flow Machine |
US5264297A (en) | 1990-03-09 | 1993-11-23 | Kennametal Inc. | Physical vapor deposition of titanium nitride on a nonconductive substrate |
US5113582A (en) | 1990-11-13 | 1992-05-19 | General Electric Company | Method for making a gas turbine engine component |
US5409871A (en) | 1993-11-02 | 1995-04-25 | Pcc Airfoils, Inc. | Ceramic material for use in casting reactive metals |
US6228453B1 (en) | 1995-06-07 | 2001-05-08 | Lanxide Technology Company, Lp | Composite materials comprising two jonal functions and methods for making the same |
CN1314170C (en) | 1995-06-12 | 2007-05-02 | Fci公司 | Electric connector with low crosstalk and impedance control, cable set |
US6177200B1 (en) | 1996-12-12 | 2001-01-23 | United Technologies Corporation | Thermal barrier coating systems and materials |
US6924040B2 (en) | 1996-12-12 | 2005-08-02 | United Technologies Corporation | Thermal barrier coating systems and materials |
US6117560A (en) | 1996-12-12 | 2000-09-12 | United Technologies Corporation | Thermal barrier coating systems and materials |
US6284390B1 (en) | 1998-06-12 | 2001-09-04 | United Technologies Corporation | Thermal barrier coating system utilizing localized bond coat and article having the same |
US6296941B1 (en) | 1999-04-15 | 2001-10-02 | General Electric Company | Silicon based substrate with yttrium silicate environmental/thermal barrier layer |
JP2002087896A (en) | 2000-09-12 | 2002-03-27 | Mitsubishi Heavy Ind Ltd | Self-repairing high heat resistant and oxidation resistant coating film, and laminated body |
US8357454B2 (en) | 2001-08-02 | 2013-01-22 | Siemens Energy, Inc. | Segmented thermal barrier coating |
US7226672B2 (en) | 2002-08-21 | 2007-06-05 | United Technologies Corporation | Turbine components with thermal barrier coatings |
US6730422B2 (en) | 2002-08-21 | 2004-05-04 | United Technologies Corporation | Thermal barrier coatings with low thermal conductivity |
US7063894B2 (en) | 2003-05-22 | 2006-06-20 | United Technologies Corporation | Environmental barrier coating for silicon based substrates |
EP1570921A1 (en) | 2004-03-02 | 2005-09-07 | Siemens Aktiengesellschaft | Process for cleaning by plasma an object |
US7509735B2 (en) | 2004-04-22 | 2009-03-31 | Siemens Energy, Inc. | In-frame repairing system of gas turbine components |
US7326441B2 (en) | 2004-10-29 | 2008-02-05 | General Electric Company | Coating systems containing beta phase and gamma-prime phase nickel aluminide |
US7638178B2 (en) | 2004-11-05 | 2009-12-29 | Honeywell International Inc. | Protective coating for ceramic components |
US20060110609A1 (en) | 2004-11-19 | 2006-05-25 | Eaton Harry E | Protective coatings |
US7374825B2 (en) | 2004-12-01 | 2008-05-20 | General Electric Company | Protection of thermal barrier coating by an impermeable barrier coating |
US7416788B2 (en) | 2005-06-30 | 2008-08-26 | Honeywell International Inc. | Thermal barrier coating resistant to penetration by environmental contaminants |
US8084086B2 (en) | 2005-06-30 | 2011-12-27 | University Of Virginia Patent Foundation | Reliant thermal barrier coating system and related methods and apparatus of making the same |
US7579085B2 (en) | 2005-08-19 | 2009-08-25 | General Electric Company | Coated silicon comprising material for protection against environmental corrosion |
US7622195B2 (en) | 2006-01-10 | 2009-11-24 | United Technologies Corporation | Thermal barrier coating compositions, processes for applying same and articles coated with same |
US7579087B2 (en) | 2006-01-10 | 2009-08-25 | United Technologies Corporation | Thermal barrier coating compositions, processes for applying same and articles coated with same |
US7722959B2 (en) | 2006-09-06 | 2010-05-25 | United Technologies Corporation | Silicate resistant thermal barrier coating with alternating layers |
US7951459B2 (en) | 2006-11-21 | 2011-05-31 | United Technologies Corporation | Oxidation resistant coatings, processes for coating articles, and their coated articles |
US7862901B2 (en) | 2006-12-15 | 2011-01-04 | General Electric Company | Yttria containing thermal barrier coating topcoat layer and method for applying the coating layer |
US20090155554A1 (en) | 2007-12-17 | 2009-06-18 | General Electric Company | Environmental barrier coating and related articles and methods |
US8062759B2 (en) | 2007-12-27 | 2011-11-22 | General Electric Company | Thermal barrier coating systems including a rare earth aluminate layer for improved resistance to CMAS infiltration and coated articles |
US20090186237A1 (en) | 2008-01-18 | 2009-07-23 | Rolls-Royce Corp. | CMAS-Resistant Thermal Barrier Coatings |
EP2128299B1 (en) | 2008-05-29 | 2016-12-28 | General Electric Technology GmbH | Multilayer thermal barrier coating |
FR2932176B1 (en) | 2008-06-06 | 2012-02-03 | Snecma Propulsion Solide | METHOD FOR PRODUCING A SELF-HEATING LAYER ON A PIECE OF COMPOSITE C / C MATERIAL |
US8111078B1 (en) | 2008-08-18 | 2012-02-07 | Xiaodong Sun Yang | Oxidizing power sensor for corrosion monitoring |
US8470460B2 (en) | 2008-11-25 | 2013-06-25 | Rolls-Royce Corporation | Multilayer thermal barrier coatings |
US8124252B2 (en) | 2008-11-25 | 2012-02-28 | Rolls-Royce Corporation | Abradable layer including a rare earth silicate |
US20100129673A1 (en) | 2008-11-25 | 2010-05-27 | Rolls-Royce Corporation | Reinforced oxide coatings |
US8343589B2 (en) | 2008-12-19 | 2013-01-01 | General Electric Company | Methods for making environmental barrier coatings and ceramic components having CMAS mitigation capability |
US8039113B2 (en) | 2008-12-19 | 2011-10-18 | General Electric Company | Environmental barrier coatings providing CMAS mitigation capability for ceramic substrate components |
US8658255B2 (en) | 2008-12-19 | 2014-02-25 | General Electric Company | Methods for making environmental barrier coatings and ceramic components having CMAS mitigation capability |
US8119247B2 (en) | 2008-12-19 | 2012-02-21 | General Electric Company | Environmental barrier coatings providing CMAS mitigation capability for ceramic substrate components |
US8658291B2 (en) | 2008-12-19 | 2014-02-25 | General Electric Company | CMAS mitigation compositions, environmental barrier coatings comprising the same, and ceramic components comprising the same |
US8273470B2 (en) | 2008-12-19 | 2012-09-25 | General Electric Company | Environmental barrier coatings providing CMAS mitigation capability for ceramic substrate components |
US20100154422A1 (en) | 2008-12-19 | 2010-06-24 | Glen Harold Kirby | Cmas mitigation compositions, environmental barrier coatings comprising the same, and ceramic components comprising the same |
FR2940278B1 (en) | 2008-12-24 | 2011-05-06 | Snecma Propulsion Solide | ENVIRONMENTAL BARRIER FOR REFRACTORY SUBSTRATE CONTAINING SILICON |
US8287635B2 (en) | 2009-02-10 | 2012-10-16 | Green Product Solutions, Inc. | Asphalt mix workable at ambient temperatures with only biodegradable solvents and method of manufacturing the same |
US8852720B2 (en) | 2009-07-17 | 2014-10-07 | Rolls-Royce Corporation | Substrate features for mitigating stress |
US8673400B2 (en) | 2009-07-31 | 2014-03-18 | General Electric Company | Methods of improving surface roughness of an environmental barrier coating and components comprising environmental barrier coatings having improved surface roughness |
JP5767248B2 (en) | 2010-01-11 | 2015-08-19 | ロールス−ロイス コーポレイション | Features to reduce thermal or mechanical stress on environmental barrier coatings |
US9315905B2 (en) | 2010-03-04 | 2016-04-19 | United Technologies Corporation | Coated article and coating process therefor |
US8337989B2 (en) | 2010-05-17 | 2012-12-25 | United Technologies Corporation | Layered thermal barrier coating with blended transition |
US9945036B2 (en) | 2011-03-22 | 2018-04-17 | General Electric Company | Hot corrosion-resistant coatings and components protected therewith |
WO2012148522A1 (en) | 2011-04-26 | 2012-11-01 | Keller Compainies, Inc. | Aerogel with reduced dust, static charge, and having reduced fluidity when in granular form |
US9034479B2 (en) | 2011-10-13 | 2015-05-19 | General Electric Company | Thermal barrier coating systems and processes therefor |
US9771811B2 (en) | 2012-01-11 | 2017-09-26 | General Electric Company | Continuous fiber reinforced mesh bond coat for environmental barrier coating system |
US20130210299A1 (en) * | 2012-02-09 | 2013-08-15 | General Electric Company | Reinforced coatings and methods of making the same |
US20150111063A1 (en) | 2012-03-23 | 2015-04-23 | Massachusetts Institute Of Technology | Hydrophobic materials incorporating rare earth elements and methods of manufacture |
US20130260130A1 (en) | 2012-03-30 | 2013-10-03 | General Electric Company | Fiber-reinforced barrier coating, method of applying barrier coating to component and turbomachinery component |
US9951630B2 (en) | 2012-06-12 | 2018-04-24 | Directed Vapor Technologies International, Inc. | Self-healing environmental barrier coating |
US11047033B2 (en) | 2012-09-05 | 2021-06-29 | Raytheon Technologies Corporation | Thermal barrier coating for gas turbine engine components |
US9428650B2 (en) | 2012-12-11 | 2016-08-30 | General Electric Company | Environmental barrier coatings and methods therefor |
CA2893961C (en) | 2012-12-17 | 2022-08-30 | Chad Daniel Kleinow | Turbine blade with abradable or abrasive tip layer |
WO2014144437A1 (en) | 2013-03-15 | 2014-09-18 | Rolls-Royce Corporation | Slurry-based coating restoration |
WO2014144152A1 (en) | 2013-03-15 | 2014-09-18 | Rolls-Royce Corporation | Improved coating interface |
US20160160664A1 (en) | 2013-03-15 | 2016-06-09 | General Electric Company | Recession resistant ceramic matrix composites and environmental barrier coatings |
US10132170B2 (en) * | 2013-03-15 | 2018-11-20 | General Electric Company | Systems and method for a composite blade with fillet transition |
FR3007028B1 (en) * | 2013-06-13 | 2015-07-03 | Herakles | ENVIRONMENTAL BARRIER FOR REFRACTORY SUBSTRATE CONTAINING SILICON |
WO2014204480A1 (en) | 2013-06-21 | 2014-12-24 | United States Of America, As Represented By The Administrator Of The National Aeronautics And Space Administration | Environmental barrier coating bond coat systems |
US20150118444A1 (en) | 2013-10-31 | 2015-04-30 | General Electric Company | Methods of manufacturing silica-forming articles having engineered surfaces to enhance resistance to creep sliding under high-temperature loading |
US10179945B2 (en) | 2013-12-16 | 2019-01-15 | General Electric Company | CMAS resistant thermal barrier coatings |
EP3094490B1 (en) | 2014-01-14 | 2018-10-17 | United Technologies Corporation | Silicon oxycarbide environmental barrier coating |
US9938839B2 (en) | 2014-03-14 | 2018-04-10 | General Electric Company | Articles having reduced expansion and hermetic environmental barrier coatings and methods for their manufacture |
US20160186580A1 (en) | 2014-05-20 | 2016-06-30 | United Technologies Corporation | Calcium Magnesium Aluminosilicate (CMAS) Resistant Thermal Barrier Coating and Coating Process Therefor |
US10399911B2 (en) | 2015-01-27 | 2019-09-03 | Rolls-Royce Corporation | Forming a surface layer of a ceramic matrix composite article |
US20170342539A1 (en) | 2015-02-10 | 2017-11-30 | Nippon Yttrium Co., Ltd. | Powder for film formation and material for film formation |
JP2016150873A (en) * | 2015-02-18 | 2016-08-22 | 株式会社Ihi | Method for producing ceramic-based composite material |
DE102015205807A1 (en) | 2015-03-31 | 2016-10-06 | Siemens Aktiengesellschaft | Coating system for gas turbines |
US10822277B2 (en) | 2015-06-17 | 2020-11-03 | National Institute For Materials Science | Oxidation-induced self-healing ceramic composition containing healing activator, method for producing same, use of same, and method for enhancing functionality of oxidation-induced self-healing ceramic compositions |
US20170022113A1 (en) | 2015-07-24 | 2017-01-26 | University Of Virginia Patent Foundation D/B/A/ University Of Virginia Licensing & Ventures Group | Rare earth silicate environmental barrier coatings having improved cmas resistance |
US20170044930A1 (en) | 2015-08-14 | 2017-02-16 | General Electric Company | Hot dust resistant environmental barrier coatings |
JP7009359B2 (en) | 2015-08-18 | 2022-01-25 | ゼネラル・エレクトリック・カンパニイ | High density environment resistant coating composition |
US10494310B2 (en) | 2015-09-14 | 2019-12-03 | Rolls-Royce Corporation | Dense environmental barrier coatings |
US20170121232A1 (en) | 2015-10-30 | 2017-05-04 | Rolls-Royce Corporation | Coating interface |
US10030305B2 (en) | 2015-11-19 | 2018-07-24 | General Electric Company | Method to protect features during repair cycle |
US10308818B2 (en) | 2016-05-19 | 2019-06-04 | United Technologies Corporation | Article having coating with glass, oxygen scavenger, and metal |
US10934626B2 (en) | 2017-04-21 | 2021-03-02 | General Electric Company | Segmented environmental barrier coating systems and methods of forming the same |
US10801111B2 (en) | 2017-05-30 | 2020-10-13 | Honeywell International Inc. | Sintered-bonded high temperature coatings for ceramic turbomachine components |
US11014857B2 (en) * | 2017-09-20 | 2021-05-25 | General Electric Company | Contact interface for a composite component and methods of fabrication |
FR3072091B1 (en) | 2017-10-05 | 2020-10-02 | Safran | ROOM PROTECTED BY AN ENVIRONMENTAL BARRIER |
US11668198B2 (en) | 2018-08-03 | 2023-06-06 | Raytheon Technologies Corporation | Fiber-reinforced self-healing environmental barrier coating |
US10934220B2 (en) | 2018-08-16 | 2021-03-02 | Raytheon Technologies Corporation | Chemical and topological surface modification to enhance coating adhesion and compatibility |
US20200080430A1 (en) | 2018-09-11 | 2020-03-12 | United Technologies Corporation | Compositional control of protective layers |
EP3640229B1 (en) | 2018-10-18 | 2023-04-05 | Rolls-Royce Corporation | Cmas-resistant barrier coatings |
US20220112608A1 (en) | 2020-08-14 | 2022-04-14 | Raytheon Technologies Corporation | Environmental barrier coating |
US11866379B2 (en) | 2020-08-14 | 2024-01-09 | Rtx Corporation | Hafnon and zircon environmental barrier coatings for silicon-based components |
-
2018
- 2018-08-03 US US16/054,015 patent/US11668198B2/en active Active
-
2019
- 2019-08-02 EP EP19189903.8A patent/EP3604257B1/en active Active
Also Published As
Publication number | Publication date |
---|---|
EP3604257A1 (en) | 2020-02-05 |
US11668198B2 (en) | 2023-06-06 |
US20200040746A1 (en) | 2020-02-06 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP3604257B1 (en) | Article comprising a fiber-reinforced self-healing bond coat | |
US6759151B1 (en) | Multilayer article characterized by low coefficient of thermal expansion outer layer | |
JP5341404B2 (en) | Articles for use at high temperature and manufacturing method | |
US6733908B1 (en) | Multilayer article having stabilized zirconia outer layer and chemical barrier layer | |
US7323247B2 (en) | Oxidation barrier coatings for silicon based ceramics | |
JP6412024B2 (en) | High temperature resistant ceramic matrix composite and environmental protection coating | |
EP2537822B1 (en) | Composite article including layer comprising silicon oxycarbide | |
JP5759383B2 (en) | Environmentally resistant coating providing CMAS reduction performance for ceramic substrate parts | |
US20190093497A1 (en) | Low porosity abradable coating | |
US7407718B2 (en) | Thermal/environmental barrier coating system for silicon-containing materials | |
EP3252278B1 (en) | High temperature composites with enhanced matrix | |
US11713283B2 (en) | Part comprising a substrate and an environmental barrier | |
US11459650B2 (en) | Oxidation resistant bond coat layers, processes for coating articles, and their coated articles | |
JP2006028015A (en) | Article including environmental barrier wall coating system and method for manufacturing the same | |
US20140255680A1 (en) | Environmental barrier coating-based thermal barrier coatings for ceramic matrix composites | |
US20070292624A1 (en) | Low conductivity, thermal barrier coating system for ceramic matrix composite (CMC) articles | |
JP2012512807A (en) | Environmentally resistant coating providing CMAS reduction performance for ceramic substrate parts | |
US20130210299A1 (en) | Reinforced coatings and methods of making the same | |
US11505508B2 (en) | Part comprising a substrate and an environmental barrier | |
EP3623355A1 (en) | Compositional control of protective layers | |
US11905222B2 (en) | Environmental barrier coating for enhanced resistance to attack by molten silicate deposits | |
EP3611149A1 (en) | Self-healing environmental barrier coating | |
EP3611151B1 (en) | Environmental barrier coating for enhanced resistance to attack by molten silicate deposits |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
AX | Request for extension of the european patent |
Extension state: BA ME |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE |
|
17P | Request for examination filed |
Effective date: 20200805 |
|
RBV | Designated contracting states (corrected) |
Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: RAYTHEON TECHNOLOGIES CORPORATION |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: GRANT OF PATENT IS INTENDED |
|
RIC1 | Information provided on ipc code assigned before grant |
Ipc: C04B 111/00 20060101ALN20211001BHEP Ipc: F01D 5/28 20060101ALI20211001BHEP Ipc: C04B 41/89 20060101ALI20211001BHEP Ipc: C04B 41/52 20060101ALI20211001BHEP Ipc: C04B 41/45 20060101ALI20211001BHEP Ipc: C04B 41/00 20060101AFI20211001BHEP |
|
INTG | Intention to grant announced |
Effective date: 20211108 |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE PATENT HAS BEEN GRANTED |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: EP |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: REF Ref document number: 1481215 Country of ref document: AT Kind code of ref document: T Effective date: 20220415 |
|
REG | Reference to a national code |
Ref country code: IE Ref legal event code: FG4D |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R096 Ref document number: 602019013310 Country of ref document: DE |
|
REG | Reference to a national code |
Ref country code: LT Ref legal event code: MG9D |
|
REG | Reference to a national code |
Ref country code: NL Ref legal event code: MP Effective date: 20220406 |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: MK05 Ref document number: 1481215 Country of ref document: AT Kind code of ref document: T Effective date: 20220406 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: NL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220406 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: SE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220406 Ref country code: PT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220808 Ref country code: NO Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220706 Ref country code: LT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220406 Ref country code: HR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220406 Ref country code: GR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220707 Ref country code: FI Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220406 Ref country code: ES Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220406 Ref country code: BG Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220706 Ref country code: AT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220406 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: RS Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220406 Ref country code: PL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220406 Ref country code: LV Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220406 Ref country code: IS Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220806 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R097 Ref document number: 602019013310 Country of ref document: DE |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: SM Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220406 Ref country code: SK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220406 Ref country code: RO Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220406 Ref country code: EE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220406 Ref country code: DK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220406 Ref country code: CZ Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220406 |
|
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
26N | No opposition filed |
Effective date: 20230110 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: MC Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220406 Ref country code: AL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220406 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PL |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: LU Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20220802 Ref country code: LI Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20220831 Ref country code: CH Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20220831 |
|
REG | Reference to a national code |
Ref country code: BE Ref legal event code: MM Effective date: 20220831 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: SI Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220406 |
|
P01 | Opt-out of the competence of the unified patent court (upc) registered |
Effective date: 20230521 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: IE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20220802 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: BE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20220831 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20230720 Year of fee payment: 5 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20230720 Year of fee payment: 5 Ref country code: DE Payment date: 20230720 Year of fee payment: 5 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: IT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20220406 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: HU Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO Effective date: 20190802 |